Balancing flyweight, rotor disk equipped therewith, rotor and aircraft engine comprising them

Abstract

The balancing flyweight of a turbomachine rotor includes two pyramid shaped end parts each one having a base and an apex, and an intermediate part which connects the two bases of the end parts together. The two apexes are aligned on a longitudinal axis. The two end parts and the intermediate part exhibit, in cross section through a plane perpendicular to said the longitudinal axis, cross-sections having polygonal shapes centered on said longitudinal axis.

1. A rotor disk of a turbomachine, said disk comprising:
 cells, said cells having two active sides; 
 blade roots which are inserted in the cells which form a gap between the blade roots in a direction tangential to the disk; and 
 at least one balancing flyweight disposed in said gap, 
 wherein the balancing flyweight comprises first and second pyramid-shaped end parts each of the first and second pyramid-shaped end parts including a base and an apex, and an intermediate part which connects the two bases of the first and second end parts together. 
 
   
   
     2. The rotor disk as claimed in  claim 1 , wherein said two apexes are aligned on a longitudinal axis. 
   
   
     3. The rotor disk as claimed in  claim 2 , wherein the balancing flyweight comprises a plane of symmetry perpendicular to said longitudinal axis. 
   
   
     4. The rotor disk as claimed in  claim 1 , wherein the balancing flyweight includes a hollow. 
   
   
     5. The rotor disk as claimed in  claim 4 , wherein said hollow is a traversing hole oriented in a direction perpendicular to a longitudinal axis which connects the two apexes. 
   
   
     6. The rotor disk as claimed in  claim 2 , wherein the two end parts and the intermediate part exhibit, in cross section through a plane perpendicular to said longitudinal axis, cross-sections having polygonal shapes centered on said longitudinal axis. 
   
   
     7. The rotor disk as claimed in  claim 6 , wherein said polygons are four sided polygons, such that each end part has the shape of a pyramid with four faces and such that the intermediate part has the shape of a parallelepiped. 
   
   
     8. The rotor disk as claimed in  claim 7 , wherein said four-sided polygons are rectangles. 
   
   
     9. The rotor disk as claimed in  claim 7 , wherein said four-sided polygons are squares. 
   
   
     10. The rotor disk as claimed in  claim 9 , wherein the balancing flyweight includes eight active faces which are the eight faces of the two end parts. 
   
   
     11. The rotor disk as claimed  claim 1 , wherein the balancing flyweight has rounded edges and rounded apexes. 
   
   
     12. The rotor disk as claimed in  claim 1 , wherein the balancing flyweight includes at least one of a nickel-based alloy, titanium-based alloy, aluminum-based alloy or steel. 
   
   
     13. The rotor disk as claimed in  claim 1 , wherein said balancing flyweight comprises two active faces disposed on one of the end parts. 
   
   
     14. The rotor disk as claimed in  claim 13 , wherein the two active faces are symmetrical with each other with respect to a median plane perpendicular to a longitudinal axis which connects the two apexes of the flyweight. 
   
   
     15. The rotor disk as claimed in  claim 14 , wherein said active faces respectively come into contact with one of the active sides of the cell when said rotor disk is driven in rotation. 
   
   
     16. A turbomachine rotor comprising at least one rotor disk as claimed in  claim 1 . 
   
   
     17. A turbomachine, comprising at least one rotor disk as claimed in  claim 1 . 
   
   
     18. An aircraft engine comprising at least one rotor disk as claimed in  claim 1 . 
   
   
     19. The rotor disk as claimed in  claim 14 , wherein an angle of inclination between the longitudinal axis and one of the active faces is between 30 degrees and 60 degrees.